Path: Orbit/OrbitMechanics
% Compute perturbations due to other planets aside from the center. Includes the ephemeris of the bodies. Currently only a center at the Earth or the Moon is supported with Earth, Moon, and sun perturbations. Has a demo for GEO orbit around the Earth. -------------------------------------------------------------------------- Form: a = PlanetaryAccelerations( r, jD, center ) -------------------------------------------------------------------------- ------ Inputs ------ r (3,1) Position vector wrt center jD (1,1) Julian Date center (1,:) Center, 'earth' or 'moon' ------- Outputs ------- a (3,1) Acceleration -------------------------------------------------------------------------- See also SunV1, MoonV1, and APlanet. --------------------------------------------------------------------------
Orbit: OrbitMechanics/APlanet SC: Ephem/MoonV1 SC: Ephem/SunV1 Common: Database/Constant Common: Time/Date2JD
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